Inlets for gas turbine engine bypass duct heat exchangers
US12071913B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 31, 2023 |
| Grant date | Aug 27, 2024 |
| Priority date | — |
| Expiry date | Jul 31, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/213
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly. The inlet cowl includes a cowl duct configured to collect a first portion of the bypass air and conduct the first portion of the bypass air into the heat exchanger and a flow diverter that guides a second portion of the bypass air around the heat exchanger.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.